A new thermal protection system by opposing jet for reusable launch vehicles

Kentaro Hayashi, Shigeru Aso, Yasuhiro Tani

研究成果: Contribution to conferencePaper査読

1 被引用数 (Scopus)

抄録

A numerical study on a reduction of aerodynamic heating by opposing jet in supersonic flow has been conducted. Flow field around a hemisphere model is calculated in supersonic free stream of Mach number 3.98 and the coolant gas is injected through the sonic nozzle at the nose of the model. In numerical analysis, axisymmetric Navier-Stokes equations are solved by an implicit finite difference method, and k-co turbulence model is used. According to the investigation of various conditions of opposing jet, important phenomena of flow field and some effective jet conditions are found. It becomes clear that a performance of the thermal protection system by opposing jet is greatly affected by jet conditions.

本文言語英語
ページ5322-5332
ページ数11
出版ステータス出版済み - 12 1 2005
イベントInternational Astronautical Federation - 56th International Astronautical Congress 2005 - Fukuoka, 日本
継続期間: 10 17 200510 21 2005

その他

その他International Astronautical Federation - 56th International Astronautical Congress 2005
Country日本
CityFukuoka
Period10/17/0510/21/05

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

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